Novel fuel gas generator arranged in rotor wing

Abstract

The utility model relates to a novel fuel gas generator arranged in a rotor wing. The novel fuel gas generator comprises a fuel gas generator shell, the rotor wing, a fuel gas generator inner cavity, a high-temperature tail gas inlet pipe, a boosting agent conveying pipe, a fuel gas generator outlet, a fuel gas generator inner cavity outlet and a rotor wing nozzle. High-temperature tail gas of a heavy oil piston engine in a power system is used for heating a hydrogen peroxide boosting agent, so that the hydrogen peroxide boosting agent is subjected to vaporization exothermic reaction, oxygen and water vapor are released, and the hydrogen peroxide boosting agent and unburnt oil gas in the tail gas are further burnt to generate higher-energy fuel gas; the number of connecting pieces is reduced, the structure is simple, the size is small, the weight of the wingtip jet power system is reduced, the path for conveying fuel gas to the wingtip is shortened, pressure loss and energy loss are reduced, the power-to-weight ratio of the wingtip jet power system is increased, the fuel gas generation amount of a fuel gas generator is increased, and fuel gas needed by wingtip jet is met.

Description

Technical Field

[0001] This utility model relates to the field of gas generator design technology, specifically to a novel gas generator built into a rotor. Background Technology

[0002] Gas generators have been applied in numerous fields, particularly in aerospace, such as aero engines, wingtip jet composite engines, ejector systems for scramjet engine testing systems, pump-fed liquid rocket engines, and ramjet engine heaters. Many researchers have improved the structure of gas generators and determined their stable operating range through cold testing, hot testing, and numerical simulation, thus driving the rapid development of gas generator technology. Early gas generators employed a multi-module, separate design, with independent layouts for components such as the combustion chamber, fuel supply, and cooling system. This resulted in complex structures and large volumes, and limitations due to uneven fuel mixing and high cooling requirements, making it difficult to meet the urgent needs of aerospace, energy, and other fields for lightweight design, high thrust-to-weight ratio, and low emissions.

[0003] In helicopter jet rotor propulsion systems, the rotor is typically driven by the reaction force generated by the engine's exhaust, or by airflow being guided through ducts to the rotor nozzles and ejected to generate a reaction force that drives the rotor. Both methods require a large amount of gas. Over the years, various engines have been tried to provide the air source for the rotor's jet propulsion, but each has its drawbacks. For example, rocket engines used as the main power unit for helicopters have too high a fuel consumption rate and are only suitable for short periods of time to facilitate takeoff and landing. Pulse engines have a relatively simple structure and low fuel consumption, but they are very noisy, have large dimensions, and short valve life. Ramjet engines are relatively compact and lightweight, with a shape that causes less aerodynamic damage to the blades and is also quieter, but they have a high fuel consumption and require the helicopter to reach a certain speed before they can start operating. Turbojet engines are powerful and can be used in large helicopters. Using this type of engine significantly improves flight distance and endurance, but when the engine rotor starts rotating around the rotor axis at several thousand revolutions per minute along with the blades, it generates a torque that attempts to tilt the entire engine upwards, requiring a fuselage torque balancing structure. To date, the gas supply problem for the power system of wingtip jet rotorcraft has not been well solved, especially in situations where large amounts of gas are required, such as helicopter hovering, takeoff, and landing. In scenarios where wingtip jet propulsion requires large amounts of gas, the amount of gas generated still needs to be further improved.

[0004] Based on the wingtip jet gas generator, this invention proposes a novel gas generator built into the rotor. The core of the design lies in high integration, which integrates traditional distributed modules into a compact unit, optimizes thermal management and reduces pressure loss, improves the power-to-weight ratio of the wingtip jet power system, and increases the gas generation of the gas generator to meet the gas requirements of wingtip jet. Utility Model Content

[0005] To address the shortcomings of existing technologies, this invention provides a novel integrated gas generator for the rotor. The aim is to simplify the structure of the gas generator and the wingtip jet rotor, reduce the number of connecting parts, lower the weight of the wingtip jet propulsion system itself, reduce pressure loss and energy consumption, improve the power-to-weight ratio of the wingtip jet propulsion system, and increase the gas output of the wingtip jet gas generator. This provides sufficient gas to drive the rotor rotation during vertical takeoff, landing, and hovering phases of the wingtip jet rotor helicopter. The gas generator, combined with the jet rotor, utilizes the interaction of high-temperature engine exhaust gas and propellant to generate a large amount of gas and heat to drive the wingtip jet propulsion.

[0006] This utility model is achieved through the following technical solution.

[0007] A novel gas generator integrated into a rotor includes a gas generator housing, a rotor, a gas generator cavity, a high-temperature exhaust gas inlet pipe, a propellant delivery pipe, a gas generator outlet, a gas generator cavity outlet, and a rotor nozzle. The gas generator housing, rotor, and gas generator cavity are hollow structures. The gas generator housing is located at the center of the rotor assembly. The rotor includes a straight pipe section and a curved pipe section. One end of the straight pipe section is connected to the gas generator housing, and the other end of the straight pipe section is connected to the curved pipe section. The curved pipe section is tapered, with the larger cross-sectional end of the curved pipe section connected to the straight pipe section. The smaller end of the bend section is the rotor nozzle. The gas generator cavity is located in the central area inside the gas generator housing. The propellant delivery pipe passes through the upper wall of the gas generator housing and communicates with the gas generator cavity. The propellant is introduced into the gas generator cavity through the propellant delivery pipe. The high-temperature exhaust gas inlet pipe is connected to the gas generator housing. The high-temperature exhaust gas is introduced into the gas generator housing through the high-temperature exhaust gas inlet pipe. The gas generator outlet and the gas generator cavity outlet are aligned with the straight pipe sections of the rotor on both sides. The gas generator outlet and the gas generator cavity outlet are converging.

[0008] Furthermore, the new built-in rotor gas generator has two inputs. The first input is high-temperature exhaust gas, which enters the gas generator housing through the high-temperature exhaust gas intake pipe from the engine to heat the catalytic converter. The second input is propellant, which enters the gas generator cavity through the propellant storage tank and the propellant delivery pipe. The two inputs are respectively introduced into the straight section of the rotor from the outlet of the converging gas generator and the outlet of the cavity. Under the action of the high-temperature exhaust gas, the gas is exothermically vaporized to form a high-temperature and high-pressure mixture, which is then ejected from the rotor nozzle.

[0009] Furthermore, the gas generator housing, rotor, and gas generator cavity are designed and molded as a single unit, reducing the number of connecting parts, simplifying the structure, reducing the size, and lowering the weight of the wingtip jet propulsion system itself.

[0010] Furthermore, the high-temperature exhaust gas inlet pipe (4) is rigidly connected to the bottom of the gas generator housing (1); the propellant delivery pipe (5) is rigidly connected to both the gas generator housing (1) and the gas generator inner cavity (3); and the two sides of the gas generator housing (1) are rigidly connected to the rotor (2).

[0011] Furthermore, the gas generator housing and the gas generator inner cavity are approximately spindle-shaped, spherical, or other shapes.

[0012] Furthermore, the propellant is a high concentration of hydrogen peroxide or a mixture thereof.

[0013] Furthermore, the straight pipe section is an elliptical cylindrical pipe, and the curved pipe section is a contracting elliptical cylindrical pipe.

[0014] Compared with the prior art, the advantages of this utility model are: This utility model utilizes the high-temperature exhaust gas of the heavy oil piston engine in the power system to heat the hydrogen peroxide propellant, thereby causing it to undergo a vaporization and exothermic reaction, releasing oxygen and water vapor, which further combusts with the unburned oil and gas in the exhaust gas to produce higher-energy gas. At the same time, the gas generator and rotor duct are integrated into the design, reducing the number of connecting parts, simplifying the structure, reducing the weight of the wingtip jet power system, shortening the path of gas delivery to the wingtip, reducing pressure loss and energy loss, improving the power-to-weight ratio of the wingtip jet power system, and increasing the gas generation of the gas generator to meet the gas requirements of wingtip jet. Attached Figure Description

[0015] Figure 1 This is a perspective view of the present utility model;

[0016] Figure 2 This is a partial cross-sectional view of the present invention;

[0017] In the diagram: 1. Gas generator housing; 2. Rotor; 3. Gas generator inner cavity; 4. High-temperature exhaust gas inlet pipe; 5. Propellant delivery pipe; 6. Gas generator outlet; 7. Inner cavity outlet; 8. Rotor nozzle. Detailed Implementation

[0018] The present invention will be further described below with reference to the accompanying drawings and specific embodiments, but this is not intended to limit the present invention.

[0019] like Figure 1 and Figure 2 As shown, a novel gas generator integrated into a rotor includes a gas generator housing 1, a rotor 2, a gas generator inner cavity 3, a high-temperature exhaust gas inlet pipe 4, a propellant delivery pipe 5, a gas generator outlet 6, a gas generator inner cavity outlet 7, and a rotor nozzle 8. The gas generator housing 1, rotor 2, and gas generator inner cavity 3 are hollow structures. The gas generator housing 1 is located at the center of the rotor 2. The rotor 2 includes a straight pipe section and a curved pipe section. One end of the straight pipe section is connected to the gas generator housing 1, and the other end of the straight pipe section is connected to the curved pipe section. The curved pipe section is converging, and the end with the larger cross-section of the curved pipe section is connected to the straight pipe section. The smaller end of the bend section is the rotor nozzle 8. The gas generator inner cavity 3 is located in the central area inside the gas generator housing 1. The propellant delivery pipe 5 passes through the upper wall of the gas generator housing 1 and communicates with the gas generator inner cavity 3. The propellant is introduced into the gas generator inner cavity 3 through the propellant delivery pipe 5. The high-temperature exhaust gas inlet pipe 4 is connected to the gas generator housing 1. The high-temperature exhaust gas is introduced into the gas generator housing 1 through the high-temperature exhaust gas inlet pipe 4. The gas generator outlet 6 and the gas generator inner cavity outlet 7 are aligned with the straight pipe sections of the rotor 2 on both sides. The gas generator outlet 6 and the gas generator inner cavity outlet 7 are constricted.

[0020] Furthermore, the novel built-in gas generator of the rotor has two inputs. The first input is high-temperature exhaust gas, which enters the gas generator housing 1 through the high-temperature exhaust gas inlet pipe 4 from the engine (in this embodiment, it is the high-temperature exhaust gas of a heavy oil piston engine) to heat the catalytic propellant. The second input is propellant, which enters the gas generator inner cavity 3 from the propellant storage tank through the propellant delivery pipe 5. The two inputs are respectively introduced into the straight pipe section of the rotor 2 from the converging gas generator outlet 6 and the inner cavity outlet 7. Under the action of the high-temperature exhaust gas, they release heat and vaporize to form a high-temperature and high-pressure mixture, which is ejected from the rotor nozzle 8.

[0021] Furthermore, the gas generator housing 1, rotor 2, and gas generator inner cavity 3 are designed and molded as a single unit, reducing the number of connecting parts, simplifying the structure, reducing the size, and lowering the weight of the wingtip jet propulsion system itself.

[0022] Furthermore, the high-temperature exhaust gas inlet pipe (4) is rigidly connected to the bottom of the gas generator housing (1); the propellant delivery pipe (5) is rigidly connected to both the gas generator housing (1) and the gas generator inner cavity (3); and the two sides of the gas generator housing (1) are rigidly connected to the rotor (2).

[0023] Furthermore, the gas generator housing 1 and the gas generator inner cavity 3 are approximately spindle-shaped, spherical, or other shapes.

[0024] Furthermore, the propellant is a high concentration of hydrogen peroxide or a mixture thereof.

[0025] Furthermore, the straight pipe section is an elliptical cylindrical pipe, and the curved pipe section is a contracting elliptical cylindrical pipe.

[0026] Among them, a rotary joint is provided at the connection between the high-temperature exhaust gas inlet pipe 4 and the high-temperature exhaust gas pipeline of the heavy oil piston engine, and a rotary joint is also provided at the connection between the propellant delivery pipe 5 and the propellant pipeline, so that the continuous input of high-temperature exhaust gas and propellant is not affected when the rotor rotates.

[0027] The above description is only a preferred embodiment of the present utility model and does not limit the implementation method and protection scope of the present utility model. Those skilled in the art should realize that all solutions obtained by equivalent substitutions and obvious changes made based on the description and illustrations of the present utility model should be included within the protection scope of the present utility model.

Claims

1. A novel gas generator built in a rotor characterized by, The application relates to a gas generator with a built-in rotor, which comprises a gas generator shell (1), a rotor (2), a gas generator cavity (3), a high-temperature tail gas inlet pipe (4), a propellant delivery pipe (5), a gas generator outlet (6), a gas generator cavity outlet (7) and a rotor nozzle (8), wherein the gas generator shell (1), the rotor (2) and the gas generator cavity (3) are hollow structures, the gas generator shell (1) is located at the center of the rotor (2), the rotor (2) comprises a straight pipe section and a bent pipe section, one end of the straight pipe section is connected with the gas generator shell (1), the other end of the straight pipe section is connected with the bent pipe section, the bent pipe section is of a contraction type, one end of the bent pipe section with a large cross section is connected with the straight pipe section, and the other end of the bent pipe section with a small cross section is the rotor nozzle (8), the gas generator cavity (3) is located in the inner central region of the gas generator shell (1), the propellant delivery pipe (5) penetrates through the upper wall of the gas generator shell (1) and communicates with the gas generator cavity (3), the propellant is introduced into the gas generator cavity (3) through the propellant delivery pipe (5), the high-temperature tail gas inlet pipe (4) communicates with the gas generator shell (1), and the high-temperature tail gas is introduced into the gas generator shell (1) through the high-temperature tail gas inlet pipe (4), the gas generator outlet (6) and the gas generator cavity outlet (7) are aligned with the straight pipe sections of the rotor (2) on both sides, and the gas generator outlet (6) and the gas generator cavity outlet (7) are of a contraction type.

2. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The novel gas generator with a built-in rotor has two inputs, the first input is high-temperature tail gas, the high-temperature tail gas from an engine enters the gas generator shell (1) through the high-temperature tail gas inlet pipe (4) and is used for heating the catalytic propellant, the second input is propellant, the propellant is introduced into the gas generator cavity (3) through the propellant delivery pipe (5), the two inputs are introduced into the straight pipe sections of the rotor (2) from the contraction type gas generator outlet (6) and the cavity outlet (7) respectively, are heated and vaporized under the action of the high-temperature tail gas, form high-temperature and high-pressure mixed gas, and are sprayed out at the rotor nozzle (8).

3. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The gas generator shell (1), the rotor (2) and the gas generator cavity (3) are integrally designed and formed.

4. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The high-temperature tail gas inlet pipe (4) is fixedly and rigidly connected with the lower portion of the gas generator shell (1), the propellant delivery pipe (5) is fixedly and rigidly connected with the gas generator shell (1) and the gas generator cavity (3), and the gas generator shell (1) is fixedly and rigidly connected with the rotors (2) on both sides.

5. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The gas generator shell (1) and the gas generator cavity (3) are approximately spindle-shaped or spherical.

6. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The propellant is high-concentration hydrogen peroxide or a mixture thereof.

7. A novel gas generator built-in to a rotor according to claim 1, characterized in that, The straight pipe section is an elliptic cylindrical pipe, and the bent pipe section is a contraction type elliptic cylindrical pipe.

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